EP3721118A1 - Train planetaire - Google Patents
Train planetaireInfo
- Publication number
- EP3721118A1 EP3721118A1 EP18827205.8A EP18827205A EP3721118A1 EP 3721118 A1 EP3721118 A1 EP 3721118A1 EP 18827205 A EP18827205 A EP 18827205A EP 3721118 A1 EP3721118 A1 EP 3721118A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- radially
- planetary gear
- sun gear
- cylindrical portion
- planet carrier
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000000463 material Substances 0.000 claims description 3
- 229910000831 Steel Inorganic materials 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 230000002028 premature Effects 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 229910052719 titanium Inorganic materials 0.000 description 2
- 239000010936 titanium Substances 0.000 description 2
- 230000015556 catabolic process Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H1/00—Toothed gearings for conveying rotary motion
- F16H1/28—Toothed gearings for conveying rotary motion with gears having orbital motion
- F16H1/48—Special means compensating for misalignment of axes, e.g. for equalising distribution of load on the face width of the teeth
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/08—General details of gearing of gearings with members having orbital motion
- F16H57/082—Planet carriers
Definitions
- the present invention relates to a planetary gear intended in particular for a turbomachine, such as for example a turbojet engine or a turboprop aircraft.
- a planetary gear can in particular allow to couple a fan and a shaft integral with the rotor of a compressor and / or a turbine. In this way, it is possible to adapt the speed of rotation of the fan so that it is different from the speed of rotation of the rotor of the turbine.
- a planetary gear can also be used to couple the propeller of a turboprop to a shaft coupled to the rotor of a turbine so as to adapt the speed of rotation of the propeller as needed.
- the use of such a planetary gear in a turbomachine is particularly known from US 9 038 779.
- the planetary gear comprises an internal sun gear, an external sun gear, satellites meshing with the internal sun gear and with the outer sun gear, each satellite being pivoted about a shaft, and a planet carrier supporting each shaft.
- the invention aims to remedy this drawback, reliably and inexpensively.
- the invention relates to a planetary gear comprising:
- each satellite meshing with the first sun gear and the second sun gear, each satellite being pivotally mounted around a shaft, a planet carrier supporting each shaft, characterized in that each shaft extends along an axis and has a cylindrical portion radially internal mounting on the planet carrier, a radially outer cylindrical portion around which the satellite is pivotally mounted and a flange extending radially from the radially outer cylindrical portion, the radially outer periphery of the flange being mounted on the planet carrier, the radially outer cylindrical portion and the radially inner cylindrical portion being connected to each other by a radially extending connection zone.
- the planet carrier may comprise a first radially extending annular flank and a second radially extending second flank, the first and second flanks being axially offset from one another and connected to one another. other by axially extending connecting parts.
- each shaft can be mounted on the first side of the planet carrier, the radially inner cylindrical portion of each shaft being mounted on the second side of the planet carrier.
- the first sun gear can be located radially inside the satellites, the second sun gear being located radially outside the satellites.
- the first sun gear, the second sun gear and the satellites may each comprise a first annular toothing and a second annular toothing, axially offset from one another, the first toothing of each satellite meshing with the first toothing of the first sun gear. and with the first toothing of the second sun gear, the second toothing of each satellite meshing with the second toothing of the first sun gear and with the second toothing of the second sun gear.
- the outer sun gear may comprise a first ring bearing the first toothing and a second ring bearing the second toothing.
- the planet carrier can be made of the same material as the shafts or in two different materials.
- the planet carrier and the shafts are for example made of steel or titanium.
- the planetary gear can comprise a cover in which are housed, at least in part, the planet carrier, the satellites and the shafts.
- the cover may comprise a first annular portion and a second annular portion, defining said volume.
- the inner sun gear and the outer sun gear are intended to rotate and the planet carrier and the shafts are intended to be kept stationary during operation.
- the internal sun gear can also be called solar.
- the outer planetary can also be called crown.
- the radially inner cylindrical portion and the radially outer cylindrical portion may be tubular, the thickness of the radially inner cylindrical portion being less than the thickness of the radially outer cylindrical portion.
- kc be the stiffness constant of the planet carrier and let kp be the stiffness constant of each tree, the planet carrier and the trees can be dimensioned such that 0.5.kc ⁇ kp ⁇ 2kc.
- the definitions of the stiffness constants are given below.
- the invention may also relate to a turbomachine, such as for example a turbojet or an airplane turboprop, comprising a planetary gear of the aforementioned type.
- a turbomachine such as for example a turbojet or an airplane turboprop, comprising a planetary gear of the aforementioned type.
- FIG. 1 is an exploded perspective view of a planetary gear according to one embodiment of the invention
- FIG. 1 is an axial sectional view of the planetary gear
- Figure 3 is a detail view of a portion of Figure 2;
- Figure 4 is a perspective view of a satellite shaft
- FIG. 5 schematically illustrates the deformation of the first side of the planet carrier when a force fc is applied at the edges of the openings of the first sidewall;
- Figure 6 schematically illustrates the deformation kp of a tree when a force fp is applied to the shaft.
- FIGS 1 to 4 illustrate a planetary gear 1 according to one embodiment of the invention. It comprises an internal sun gear 2 or solar, an external sun gear 3 or crown, satellites 4 pivotally mounted around shafts 5 and a planet carrier 6 on which are mounted the shafts 5 of the satellites 6.
- the sun gear 1 comprises in addition a cover 7 or crown holder.
- the inner sun gear 2 is annular axis A and has a first toothing 9a and a second toothing 9b annular and radially external, axially offset from one another.
- Each satellite 4 is annular and has a radially inner cylindrical surface 10.
- Each satellite 4 further comprises a first toothing 1 1a and a second toothing 11b annular radially external, axially offset from each other, respectively meshing with the first and second teeth 9a, 9b of the inner sun gear 2.
- the planet carrier 6 comprises a first annular flank 12 and a second annular flank 13 offset axially from one another and connected by axially extending connecting portions 14.
- the first sidewall 12 comprises circular openings 15 of axes B.
- the second sidewall 13 has holes 16 of axes B, located axially facing the circular openings 15 of the first sidewall.
- the connecting portions 14 delimit housing 17 for mounting satellites 4. Said housing 17 opens radially outwardly so as to allow the radial mounting of the satellites 4 in said housing 17 of the planet carrier 6.
- Each shaft 5 extends along the corresponding axis B and comprises a radially inner cylindrical portion 18, a radially outer cylindrical portion 19 around which the satellite 4 is pivotally mounted and a flange 20 extending radially from the portion radially outer cylindrical 19.
- the radially outer periphery of the flange 20 comprises a cylindrical rim 20a whose one end, said front end, is extended by a radial flange 20b, so as to have a generally L-shaped section.
- the outer surface of the cylindrical flange 20a is mounted without play or with a small clearance in the opening 15 of the first flank 12 of the planet carrier 6.
- the radial flange 20b bears axially on the radial front face of the first flank 12.
- Said internal cylindrical portion 18 more particularly comprises a first zone 21 or front zone, of smaller diameter than a second zone 22 or rear zone.
- the rear zone 22 is mounted without clearance or with a small clearance in the hole 16 of the second sidewall 13 of the planet carrier 6.
- the second zone 22 has an annular groove 23 at its radially outer surface.
- the outer diameter of said second zone 22 is dO.
- the thickness of the first zone 21, that is to say the radial distance between the inner surface and the outer surface of the first zone 21, is denoted eO.
- the outer diameter of the first zone 21 is denoted d3.
- the dimensions of the first zone 21 are defined to provide flexibility at said first zone 21.
- the outer diameter of the radially outer cylindrical portion 19 is denoted d1.
- the width of the radial annular portion 20 of the flange is noted I2.
- the outer diameter of the rim 20a is noted d4.
- the width I2 is defined to provide flexibility in the flange 20.
- the radially outer cylindrical portion 19 and the radially inner cylindrical portion 18 are connected to each other by a radially extending annular connection zone 24. More particularly, the connecting zone 24 connects an end, in particular the front end, of the internal cylindrical portion 18, and a median zone of the outer cylindrical portion 19. An annular space 25 is delimited between the cylindrical portion radially 18 and the radially outer cylindrical portion 19.
- the smallest width of the connecting zone 24, that is to say the smallest axial distance from the connecting zone 24, is denoted I3.
- the dimensions d0, d1, d3 and d4 are defined such that d3 ⁇ d0 ⁇ d1 ⁇ d4. Moreover, the dimensions eO and e1 are defined such that eO ⁇ e1.
- the shafts 5 and the planet carrier 6 are for example made of steel or titanium.
- Figure 5 schematically illustrates the deformation of the first sidewall 12 of the planet carrier 6 when a force fc is applied at the edges of the openings 15 and the second side 13 is defined as being fixed.
- the value of the force applied to each opening 12 is equal to fc / n, the forces being evenly distributed over the different openings 12. This force causes a displacement of each opening 12. After displacement, the openings 12 are illustrated in dashed lines.
- Figure 6 schematically illustrates the deformation dp of a shaft 5 when a force fp is applied to the shaft and the outer periphery of the flange 20 and the second zone 22 of the inner portion 18 are considered fixed .
- the flange 20 and the first zone 21 of the inner portion 18 are shown as springs, given their flexibility or flexibility.
- the dashed portions illustrate said portions after deformation.
- the outer sun gear 3 comprises a first ring 26 and a second ring 27 axially offset from one another.
- each ring 26, 27 comprises a radially inner annular portion 26a, 27a bearing a radially internal toothing 26b, 27b.
- the first ring 26 carries a first toothing 26a meshing with the first toothing 11a of each satellite 4.
- the second ring 27 carries a second toothing 27b meshing with the second toothing 11b of each satellite 4.
- Each ring 26, 27 further comprises a radially outer flange 26c, 27c extending radially.
- Each ring 26, 27 finally has an oblique connecting wall 26d, 27d connecting the outer flange 26c, 27c and the inner annular portion 26a, 27a.
- the connecting wall 26d of the first ring 26 flares towards the second ring 27.
- the connecting wall 27d of the second ring 27 flares towards the first ring 26.
- the radially inner periphery of the flange 26c the first ring 26 comprises an annular centering flange 28 engaged in a recess 29 of corresponding shape of the flange 27c of the second ring 27.
- the two flanges 26c, 27c are in axial abutment on one another.
- the cover 7 is fixed on the flanges 26c, 27c of the first and second rings 26, 27.
- the cover 7 has a first portion 30 or front portion and a second portion 31 or rear portion, each portion 30, 31 having a radial annular flange 30a, 31a at the radially outer periphery.
- the flanges 30a, 31a of the parts 30, 31 of the cover 7 are fixed axially on either side of the flanges 26c, 27c of the rings, for example by welding or bolting.
- the first and second parts 30, 31 of the cover 7 define an annular internal volume housing, at least in part, the satellites 4, the shafts 5 and the planet carrier 6.
- the planetary gear 1 can make it possible to transmit a large torque which may have the effect of slightly deforming the planet carrier 6, in particular at the level of the second sidewall 13.
- the structure of the shafts 5 allows them to deform, at flange 20, the cylindrical parts 18, 19 or the connection zone 24, in order to compensate for the deformations of the planet carrier 6. This maintains good meshing performance between the satellites 4 and the planet wheels 2, 3 while avoiding premature wear of the teeth 9a, 9b, 11a, 11b, 27a, 27b .
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Retarders (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1761793A FR3074871B1 (fr) | 2017-12-07 | 2017-12-07 | Train planetaire |
PCT/FR2018/053043 WO2019110892A1 (fr) | 2017-12-07 | 2018-11-29 | Train planetaire |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3721118A1 true EP3721118A1 (fr) | 2020-10-14 |
EP3721118B1 EP3721118B1 (fr) | 2021-12-29 |
Family
ID=61187500
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP18827205.8A Active EP3721118B1 (fr) | 2017-12-07 | 2018-11-29 | Train planetaire |
Country Status (6)
Country | Link |
---|---|
US (1) | US11028902B2 (fr) |
EP (1) | EP3721118B1 (fr) |
JP (1) | JP2021505825A (fr) |
CN (1) | CN111433492B (fr) |
FR (1) | FR3074871B1 (fr) |
WO (1) | WO2019110892A1 (fr) |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1448059A (en) | 1974-04-18 | 1976-09-02 | Vickers Ltd | Gears |
FR2713732B1 (fr) * | 1993-12-15 | 1996-01-12 | Hispano Suiza Sa | Transmission à engrenages orbitaux et charge répartie. |
IT1308368B1 (it) * | 1999-02-12 | 2001-12-17 | Fiatavio Spa | Perno per il collegamento di ruote dentate ad un organo di supporto etrasmissione provvista di tale perno. |
US20030008748A1 (en) * | 2001-06-28 | 2003-01-09 | Gerald Fox | Epicyclic gear system |
JP2009108996A (ja) * | 2007-11-01 | 2009-05-21 | Toyota Motor Corp | プラネタリギヤ装置ならびに車両用トランスアクスル |
ES2384548T3 (es) * | 2007-12-19 | 2012-07-06 | Gamesa Innovation & Technology, S.L. | Portaplanetas para una etapa planetaria con una placa bogie |
DE102008063044B4 (de) * | 2008-12-23 | 2012-01-05 | Aerodyn Engineering Gmbh | Planetengetriebe |
ITTO20111202A1 (it) * | 2011-12-23 | 2013-06-24 | Avio Spa | Rotismo epicicloidale |
DE102012208799A1 (de) * | 2012-05-25 | 2013-11-28 | Schaeffler Technologies AG & Co. KG | Stütz- und Führungsscheibe in einem Planetentrieb |
US9328818B2 (en) | 2012-09-21 | 2016-05-03 | United Technologies Corporation | Gear carrier flex mount lubrication |
ITMI20121712A1 (it) * | 2012-10-11 | 2014-04-12 | Danieli Off Mecc | Riduttore epicicloidale |
US9038779B2 (en) | 2013-08-30 | 2015-05-26 | United Technologies Corporation | Geared architecture gas turbine engine with oil scavenge |
DE102013217522A1 (de) * | 2013-09-03 | 2015-03-19 | Schaeffler Technologies AG & Co. KG | Planetenkoppelgetriebe |
FR3011901B1 (fr) * | 2013-10-10 | 2017-02-10 | Hispano-Suiza | Porte-satellites pour un reducteur de vitesse a train epicycloidal |
US20160025187A1 (en) * | 2014-07-25 | 2016-01-28 | Caterpillar Inc. | Planetary gear system |
-
2017
- 2017-12-07 FR FR1761793A patent/FR3074871B1/fr active Active
-
2018
- 2018-11-29 JP JP2020530996A patent/JP2021505825A/ja active Pending
- 2018-11-29 WO PCT/FR2018/053043 patent/WO2019110892A1/fr unknown
- 2018-11-29 CN CN201880078812.4A patent/CN111433492B/zh active Active
- 2018-11-29 EP EP18827205.8A patent/EP3721118B1/fr active Active
- 2018-11-29 US US16/770,212 patent/US11028902B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
CN111433492B (zh) | 2023-11-10 |
US11028902B2 (en) | 2021-06-08 |
US20200386299A1 (en) | 2020-12-10 |
EP3721118B1 (fr) | 2021-12-29 |
WO2019110892A1 (fr) | 2019-06-13 |
FR3074871A1 (fr) | 2019-06-14 |
CN111433492A (zh) | 2020-07-17 |
JP2021505825A (ja) | 2021-02-18 |
FR3074871B1 (fr) | 2019-12-13 |
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